EP2310741A2 - Fuel insert - Google Patents

Fuel insert

Info

Publication number
EP2310741A2
EP2310741A2 EP09779477A EP09779477A EP2310741A2 EP 2310741 A2 EP2310741 A2 EP 2310741A2 EP 09779477 A EP09779477 A EP 09779477A EP 09779477 A EP09779477 A EP 09779477A EP 2310741 A2 EP2310741 A2 EP 2310741A2
Authority
EP
European Patent Office
Prior art keywords
fuel
nozzle
receiving unit
nozzle insert
burner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP09779477A
Other languages
German (de)
French (fr)
Other versions
EP2310741B1 (en
Inventor
Thomas Grieb
Bernd Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP09779477.0A priority Critical patent/EP2310741B1/en
Publication of EP2310741A2 publication Critical patent/EP2310741A2/en
Application granted granted Critical
Publication of EP2310741B1 publication Critical patent/EP2310741B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means

Definitions

  • the present invention relates to a fuel nozzle for the twisting of a fuel / air-fuel mixture.
  • the invention further relates to a burner and a gas turbine.
  • Gas turbines are known to have the following components: a compressor for compressing air; a combustion chamber for generating hot gas by burning fuel in the presence of the compressed air supplied from the compressor; and a turbine in which the hot gas supplied from the combustion chamber is expanded.
  • Gas turbines are known to emit undesirable nitrogen oxides (NOx) and carbon monoxide (CO).
  • NOx nitrogen oxides
  • CO carbon monoxide
  • One known factor affecting NOx emissions is the combustion temperature. If the combustion temperature is lowered, the amount of NOx released decreases. However, high combustion temperatures are desirable to achieve high efficiency. It is known that leaner fuel / air mixtures burn cooler and therefore less NOx emissions arise.
  • One known technique for producing a leaner fuel mixture is to create turbulence to mix air and fuel as evenly as possible prior to combustion to avoid creating zones of rich mixture in which there are high temperature localities (so-called hot spots).
  • fuel is flowed in via a so-called Swirler.
  • compressed air is supplied through a channel of the combustion chamber.
  • Swirler are arranged, which are connected to a fuel line.
  • These swirlers twist the combustion air and at the same time introduce fuel into the combustion air through holes in the swirl blades.
  • This mixture then flows to the combustion chamber to be burned there.
  • This system becomes a as homogeneous as possible mixture of fuel to air, which contributes significantly to the NOx reduction.
  • a first object of the present invention to provide a fuel nozzle which overcomes the above-mentioned problems.
  • a second object of the present invention is the disclosure of an advantageous burner. It is a third object of the invention to provide an advantageous gas turbine.
  • the first object is achieved by a fuel nozzle according to claim 1.
  • the second object is achieved by a burner according to claim 13.
  • the object related to the gas turbine is achieved by a gas turbine according to claim 16.
  • a component namely the nozzle insert in another component, namely the receiving unit.
  • a flow path and a swirl chamber are formed.
  • fuel in particular liquid
  • the flow path can itself take on a kind of nozzle function in that it is formed differently geometrically, for example, when stream enters the swirl chamber tapers or widened. If the fuel is accelerated in the flow path, ie the highest speed is only when it enters the pickup unit itself, too high pressure losses and cavitations can be avoided.
  • the nozzle insert At the inlet beginning of the fuel and at the end, that is to say substantially in the swirl chamber itself, the nozzle insert is bent in a substantially circular manner, and thus essentially forms a broken circle. Flow thus occurs from a flow path and into a swirl chamber in such a way that the fuel performs a circular, in particular a spiral movement in the swirl chamber.
  • the nozzle insert according to the invention thus produces a
  • the depth of the receiving unit decreases at the beginning of entry of the nozzle insert in the flow direction.
  • This causes the flow rate of the fuel to be changed, namely increased.
  • This also causes an increase in the flow velocity.
  • the flow path, which is formed by the entry start of the nozzle insert and the receiving unit, also expand in the flow direction. This also causes a change in the flow velocity.
  • simultaneous reduction of the depth of the receiving unit at the inlet beginning in the flow direction can also be done so increasing the flow velocity.
  • the nozzle insert can be used as an integrated component in the receiving unit.
  • the swirl chamber is preferably designed circular.
  • the swirl chamber may further comprise an outlet, so that the fuel twisted can escape there.
  • the outlet thus serves as a spray nozzle and may, for example, also have a tapered shape.
  • the so twisted fuel then enters the combustion chamber.
  • the outlet is a bore, in particular a transverse bore. This is particularly easy to install later.
  • the fuel nozzle arrangement comprises four-eight fuel nozzles arranged symmetrically on a disk. This disc is accordingly integrated in a customized recording unit of the essay.
  • the essay also includes four-eight outlets.
  • Fuel nozzle assembly created which is integrated into an essay and thus includes all outlets (atomizer nozzles). Thus, therefore, the fuel is divided into individual streams on its circumference.
  • the number of nozzle inserts and receiving units arranged on the disk can vary, as can the arrangement of the nozzle inserts / receiving units on the disk.
  • the nozzle insert and / or the receiving unit preferably consists of metal or a metal alloy.
  • the nozzle insert and / or the receiving unit preferably consists of metal or a metal alloy.
  • Embodiment consist of the nozzle insert and / or the receiving unit of ceramic or ceramic material, since these materials are particularly abrasion resistant.
  • the nozzle insert and / or the receiving unit are fine mechanical or with print technology produced. This production is particularly inexpensive and quick to implement.
  • Fig. 4.5 shows schematically an article 13 with 4 burner inserts according to the invention in back and front view.
  • FIG. 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft, which is also referred to as a turbine runner.
  • the combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. In the flow direction of a working medium As can be seen in the hot gas duct 111 of a guide blade row 115, a row 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • Coupled to the rotor 103 is a generator or a work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is guided to the burners 107 and mixed there with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • FIG. 2 schematically shows a section through a burner 107 with a nozzle according to the prior art in a partially perspective view.
  • the burner 107 can be used on the one hand in conjunction with the annular combustion chamber 106.
  • the burner 107 is used in conjunction with a so-called tube combustion chamber.
  • the gas turbine 100 has, instead of the annular combustion chamber 106, a plurality of annularly arranged tube combustion chambers whose outflow-side openings open into the annular hot gas channel 111 on the inlet side of the turbine.
  • a plurality of, for example six or eight, burners 107 are preferably arranged on each of these tube combustion chambers at the opposite end of the downstream opening of the tube combustion chamber, usually annularly around a pilot burner.
  • the burner 107 comprises a cylindrical housing 12.
  • a lance with a fuel channel 16 is arranged along the central axis 27 of the burner 107.
  • the latter comprises a pointed attachment 13, which is arranged concentrically to the central axis 27.
  • the fuel nozzles 1 are arranged according to the prior art, which communicate with the fuel channel 16.
  • swirl vanes 17 are arranged around the lance.
  • the swirl blades 17 are arranged along the circumference of the lance in the housing 12.
  • a compressor air flow 15 is passed into the combustion chamber 110 leading to the part of the burner 107.
  • the air is displaced by the swirl blades 17 in a swirling motion.
  • Fuel for example oil, is injected through the fuel nozzles 1 into the resulting air stream.
  • the resulting fuel-air mixture is then passed on to the combustion chamber 110.
  • FIG. 3 schematically shows a section through a fuel nozzle according to the invention.
  • the nozzle inserts 1 are arranged on the outer circumference of the attachment 13 in corresponding receiving units 4.
  • a fuel nozzle arrangement comprises a plurality of, in the present embodiment, four nozzle inserts 1 according to the invention with corresponding receiving units 4 (FIG. 4, rear view and FIG. 5 front view).
  • the flow paths 5 are indicated here as four slots (FIG. 4, FIG. 5).
  • the central axis of the attachment 13 is indicated by the reference numeral 18.
  • the attachment 13 is conical to the combustion chamber 110, tapered designed.
  • the nozzle insert 1 is arranged on the outer circumference of the attachment 13 in the corresponding receiving units 4 and thus forms the swirl chambers 10.
  • the nozzle insert 1 according to the invention is made as an integrated component.
  • the nozzle according to the invention Insert 1 comprises at its fuel inlet 2, which is located in the swirl chamber 10 approximately a semicircular curved inlet beginning 7a and an end 7b.
  • the nozzle insert 1 has a nozzle insert neck 3.
  • the nozzle insert 1, in particular the nozzle insert neck 3 itself and the preferably circularly curved inlet beginning 7a, form with the receiving unit 4 a flow path 5, along which the fuel can flow.
  • the entry start 7a and the end 7b form with the receiving unit 4, the swirl chamber 10 from.
  • the flow path 5 which through the inlet beginning 7a of the nozzle insert 1 and the receiving unit
  • the flow rate is increased.
  • the increase can also take place in that the depth of the
  • the swirl chamber 10 is essentially circular.
  • the flow path 5 thus performs at the inlet beginning 7a in the swirl chamber 10 by this arrangement a circular movement, which directs the fuel towards the outlet 8.
  • the fuel thus performs a circular movement, that is, the fuel is thus circular, in particular spiral 12 swirled.
  • the so-swirled fuel passes through the outlet 8 for the purpose of atomization.
  • the outlet 8 is a transverse bore for the purpose of outflow.
  • the nozzle insert 1 according to the invention thus generates a flow of fuel, in particular a liquid fuel flow with a swirl component in the chambers downstream.
  • a fuel nozzle is thus created by a nozzle insert 1 which can be integrated in a receiving unit 4.
  • a disk with a fuel nozzle arrangement according to the invention is provided, which is inserted into an attachment 13 or another component and thus supplies all the outlets 8 (atomization openings) of the attachment 13.
  • the fuel nozzle or the fuel nozzle arrangement divides the Brennstoffström distributed in individual streams on the circumference.
  • the previously used nozzles are used for swirl generation in the flow of the fuel before it enters the combustion chamber.
  • the twist is now generated by means of the special geometry of the fuel nozzle according to the invention.
  • the fuel nozzle or the receiving unit and / or the nozzle insert can be made of metallic or ceramic materials fine mechanical or "print" -based.
  • an acceleration of the fuel take place, so as to obtain maximum speed only at the entrance to the swirl chamber 10, so that too high pressure losses and cavitation are avoided and one thus obtains an effective nozzle cross section, which is more independent of the throughput.
  • This can be achieved, for example, by bending the inlet beginning 7a to the outlet center 8 or bending it away from the outlet center 8 and / or by changing the depth of the receiving unit 4 at the entrance beginning 7a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)

Abstract

The invention discloses a fuel nozzle for imparting swirl to a fuel/fuel-air mixture, comprising a holding unit (4) and a nozzle insert (1), wherein the nozzle insert (1) and the holding unit (4) form a flow path (5) and subsequently a swirl chamber (10), wherein the nozzle insert (1) has an inlet start (7a) and an end (7b), wherein the inlet start (7a) and the end (7b) are bent in a substantially circular manner such that an unbroken circle is formed, such that a fuel flowing into the swirl chamber (10) has imparted to it a radially inwardly directed circular, in particular spiral movement (12). The invention also discloses a burner and a gas turbine.

Description

Beschreibungdescription
BrennstoffeinsätzBrennstoffeinsätz
Die vorliegende Erfindung betrifft eine Brennstoffdüse zur Verdrallung eines Brennstoff/Brennstoff-Luft Gemisch. Die Erfindung bezieht sich weiterhin auf einen Brenner und eine Gasturbine .The present invention relates to a fuel nozzle for the twisting of a fuel / air-fuel mixture. The invention further relates to a burner and a gas turbine.
Gasturbinen besitzen bekanntlich folgende Komponenten: einen Verdichter zum Verdichten von Luft; eine Brennkammer zum Erzeugen heißen Gases durch Verbrennen von Brennstoff in Anwesenheit der vom Kompressor gelieferten, verdichteten Luft; und eine Turbine, in der das von der Brennkammer gelieferte heiße Gas entspannt wird. Gasturbinen emittieren bekanntlich unerwünschte Stickoxide (NOx) und Kohlenmonoxid (CO) . Ein bekannter Faktor, der die NOx-Emissionen beeinflusst, ist die Verbrennungstemperatur. Senkt man die Verbrennungstemperatur, so sinkt die Menge des abgegebenen NOx. Allerdings sind hohe Verbrennungstemperaturen wünschenswert, um einen hohen Wirkungsgrad zu erreichen. Es ist bekannt, dass magerere Brennstoff/Luft-Gemische kühler verbrennen und deshalb weniger NOx-Emissionen entstehen. Eine bekannte Technik zum Erzeugen eines magereren Brennstoffgemischs ist es, Turbulenzen zu er- zeugen, um Luft und Brennstoff vor der Verbrennung so gleichmäßig wie möglich zu vermischen, um zu vermeiden, das Zonen mit fettem Gemisch entstehen, in denen es örtliche Stellen hoher Temperatur gibt (so genannte Hot Spots) . Bei can, can annular, annular Systemen wird deshalb Brenn- Stoff über einen sogenannten Swirler eingeströmt. Hierbei wird verdichtete Luft durch einen Kanal der Brennkammer zugeführt. In diesem Kanal werden Swirler angeordnet, welche mit einer Brennstoffleitung verbunden sind. Diese Swirler verdrallen die Verbrennungsluft und bringen gleichzeitig über Bohrungen in den Swirlerblättern Brennstoff in die Verbrennungsluft ein. Dieses Gemisch strömt dann der Brennkammer zu, um dort verbrannt zu werden. Durch dieses System wird eine möglichst homogene Durchmischung von Kraftstoff zu Luft erzielt, was wesentlich zur NOx Reduktion beiträgt.Gas turbines are known to have the following components: a compressor for compressing air; a combustion chamber for generating hot gas by burning fuel in the presence of the compressed air supplied from the compressor; and a turbine in which the hot gas supplied from the combustion chamber is expanded. Gas turbines are known to emit undesirable nitrogen oxides (NOx) and carbon monoxide (CO). One known factor affecting NOx emissions is the combustion temperature. If the combustion temperature is lowered, the amount of NOx released decreases. However, high combustion temperatures are desirable to achieve high efficiency. It is known that leaner fuel / air mixtures burn cooler and therefore less NOx emissions arise. One known technique for producing a leaner fuel mixture is to create turbulence to mix air and fuel as evenly as possible prior to combustion to avoid creating zones of rich mixture in which there are high temperature localities (so-called hot spots). In can, can annular, annular systems, therefore, fuel is flowed in via a so-called Swirler. Here, compressed air is supplied through a channel of the combustion chamber. In this channel Swirler are arranged, which are connected to a fuel line. These swirlers twist the combustion air and at the same time introduce fuel into the combustion air through holes in the swirl blades. This mixture then flows to the combustion chamber to be burned there. This system becomes a as homogeneous as possible mixture of fuel to air, which contributes significantly to the NOx reduction.
Bei Verbrennungsmaschinen, insbesondere solchen, die mit zwei verschiedenen Brennstoffen betrieben werden, erfolgt beispielsweise eine Eindüsung des Brennstoffes Öl über Drallerzeuger, in denen das Öl mit Luft vermischt wird. Zur besseren Zerstäubung und Vermischung von Öl und Luft kann das Öl innerhalb der zur Eindüsung verwendeten Düsen in eine Drallbe- wegung versetzt werden. Diese Drallerzeugung innerhalb der Öldüse wird bisher dadurch erreicht, dass diese Düsen aus mehreren Plättchen, welche an geringfügig voneinander abweichenden Koordinaten Bohrungen aufweisen, bestehen. Durch das Zusammenlöten der einzelnen Plättchen entsteht eine Spirale, welche zur Drallgebung des Brennstoffes genutzt wird. Allerdings weisen solche Düsen einen konstruktiv aufwendigen Aufbau auf, da die Bohrungen exakt platziert werden müssen.In combustion engines, in particular those which are operated with two different fuels, for example, an injection of the fuel oil via swirl generator, in which the oil is mixed with air. For better atomization and mixing of oil and air, the oil can be placed in a swirling motion within the nozzles used for injection. This swirl generation within the oil nozzle has hitherto been achieved in that these nozzles consist of a plurality of platelets which have bores at slightly different coordinates. By soldering together the individual platelets creates a spiral, which is used to spin the fuel. However, such nozzles have a structurally complex construction, since the holes must be placed accurately.
Es ist daher eine erste Aufgabe der vorliegenden Erfindung, eine Brennstoffdüse zur Verfügung zu stellen, die die oben genannten Schwierigkeiten beseitigt. Eine zweite Aufgabe der vorliegenden Erfindung besteht in der Offenbarung eines vorteilhaften Brenners. Es ist eine dritte Aufgabe der Erfindung, eine vorteilhafte Gasturbine zur Verfügung zu stellen.It is therefore a first object of the present invention to provide a fuel nozzle which overcomes the above-mentioned problems. A second object of the present invention is the disclosure of an advantageous burner. It is a third object of the invention to provide an advantageous gas turbine.
Die erste Aufgabe wird durch eine Brennstoffdüse nach Anspruch 1 gelöst. Die zweite Aufgabe wird durch einen Brenner nach Anspruch 13 gelöst. Die auf die Gasturbine bezogene Aufgabe wird durch eine Gasturbine nach Anspruch 16 gelöst. Die abhängigen Ansprüche beinhalten weitere, vorteilhafte Ausgestaltungen der Erfindung.The first object is achieved by a fuel nozzle according to claim 1. The second object is achieved by a burner according to claim 13. The object related to the gas turbine is achieved by a gas turbine according to claim 16. The dependent claims contain further, advantageous embodiments of the invention.
Erfindungsgemäß wird hier also vorgeschlagen, ein Bauteil, nämlich den Düseneinsatz in ein anderes Bauteil nämlich die Aufnahmeneinheit anzuordnen. Dadurch werden ein Strömungspfad und eine Drallkammer ausgebildet. Somit ist eine einfachere Installation der erfindungsgemäßen „Düse" möglich. Durch den Strömungspfad strömt somit Brennstoff, insbesondere Flüssig- brennstoff. Der Strömungspfad kann dabei selber eine Art Düsenfunktion übernehmen, indem er unterschiedlich geometrisch geformt wird, z.B. bei Stromeintritt in die Drallkammer sich verjüngt oder verbreitert. Wird der Brennstoff in dem Strö- mungspfad beschleunigt, das heißt die größte Geschwindigkeit ist erst bei Eintritt in die Aufnahmeneinheit selber, können so zu hohe Druckverluste und Kavitationen vermieden werden. Am Eintrittsanfang des Brennstoffs sowie am Ende, das heißt im Wesentlichen in der Drallkammer selber, ist der Düsenein- satz im Wesentlichen kreisförmig gebogen, und bildet somit im wesentlichen einen unterbrochenen Kreis. Strömung tritt hier also aus einem Strömungspfad aus und in eine Drallkammer ein und zwar dergestalt, dass der Brennstoff eine kreis-, insbesondere eine spiralförmige Bewegung in der Drallkammer aus- führt. Der erfindungsgemäße Düseneinsatz erzeugt so eineAccording to the invention, it is therefore proposed here to arrange a component, namely the nozzle insert in another component, namely the receiving unit. Thereby, a flow path and a swirl chamber are formed. Thus, a simpler installation of the "nozzle" according to the invention is possible, so that fuel, in particular liquid, flows through the flow path. fuel. The flow path can itself take on a kind of nozzle function in that it is formed differently geometrically, for example, when stream enters the swirl chamber tapers or widened. If the fuel is accelerated in the flow path, ie the highest speed is only when it enters the pickup unit itself, too high pressure losses and cavitations can be avoided. At the inlet beginning of the fuel and at the end, that is to say substantially in the swirl chamber itself, the nozzle insert is bent in a substantially circular manner, and thus essentially forms a broken circle. Flow thus occurs from a flow path and into a swirl chamber in such a way that the fuel performs a circular, in particular a spiral movement in the swirl chamber. The nozzle insert according to the invention thus produces a
Drallkomponente in der Drallkammer, insbesondere auch in der Brennkammer stromab.Swirl component in the swirl chamber, in particular in the combustion chamber downstream.
Bevorzugt verringert sich die Tiefe der Aufnahmeneinheit am Eintrittsanfang des Düseneinsatzes in Strömungsrichtung. Dies bewirkt, dass sich die Strömungsgeschwindigkeit des Brennstoff verändert, nämlich erhöht. Und/oder kann sich auch der Strömungspfad, welcher durch den Eintrittsanfang des Düseneinsatzes und die Aufnahmeeinheit gebildet wird, in Strö- mungsrichtung verjüngen. Dies bewirkt ebenfalls eine Erhöhung der Strömungsgeschwindigkeit. Alternativ kann sich der Strömungspfad, welcher durch den Eintrittsanfang des Düseneinsatzes und die Aufnahmeeinheit gebildet wird, in Strömungsrichtung auch erweitern. Dies bewirkt ebenfalls eine Änderung der Strömungsgeschwindigkeit. Bei gleichzeitiger Verringerung der Tiefe der Aufnahmeneinheit am Eintrittsanfang in Strömungsrichtung kann auch so eine Erhöhung der Strömungsgeschwindigkeit erfolgen.Preferably, the depth of the receiving unit decreases at the beginning of entry of the nozzle insert in the flow direction. This causes the flow rate of the fuel to be changed, namely increased. And / or the flow path, which is formed by the entry start of the nozzle insert and the receiving unit, taper in the flow direction. This also causes an increase in the flow velocity. Alternatively, the flow path, which is formed by the entry start of the nozzle insert and the receiving unit, also expand in the flow direction. This also causes a change in the flow velocity. With simultaneous reduction of the depth of the receiving unit at the inlet beginning in the flow direction can also be done so increasing the flow velocity.
Bevorzugt ist der Düseneinsatz als integriertes Bauteil in die Aufnahmeneinheit einsetzbar. Die Drallkammer ist bevorzugt kreisförmig ausgestaltet. Somit kann der Brennstoffein- lass mit seinen halbkreisförmig gebogenen Eintrittsanfang und Ende besonders stabil in die Aufnahmeneinheit integriert werden. Aber auch andere geometrische Formen sind vorstellbar. Die Drallkammer kann weiterhin einen Auslass umfassen, so dass der Brennstoff verdrallt dort austreten kann. Der Aus- lass dient somit als Zerstäuberdüse und kann z.B. ebenfalls eine sich verjüngende Form aufweisen. Der so verdrallte Brennstoff tritt dann in die Brennkammer ein. Bevorzugt ist der Auslass eine Bohrung, insbesondere eine Querbohrung. Diese ist besonders einfach auch nachträglich noch anzubringen. In bevorzugter Ausgestaltung sind als Brennstoffdüsenanord- nung vier -acht symmetrisch auf einer Scheibe angeordnete Brennstoffdüsen umfasst. Diese Scheibe wird dementsprechend in einer angepassten Aufnahmeneinheit des Aufsatzes integriert. Der Aufsatz umfasst dabei im Wesentlichen ebenfalls vier -acht Auslässe. Somit wird also erfindungsgemäß einePreferably, the nozzle insert can be used as an integrated component in the receiving unit. The swirl chamber is preferably designed circular. Thus, the fuel inlet with its semicircular curved inlet beginning and End are particularly stable integrated into the recording unit. But other geometric shapes are conceivable. The swirl chamber may further comprise an outlet, so that the fuel twisted can escape there. The outlet thus serves as a spray nozzle and may, for example, also have a tapered shape. The so twisted fuel then enters the combustion chamber. Preferably, the outlet is a bore, in particular a transverse bore. This is particularly easy to install later. In a preferred embodiment, the fuel nozzle arrangement comprises four-eight fuel nozzles arranged symmetrically on a disk. This disc is accordingly integrated in a customized recording unit of the essay. Essentially, the essay also includes four-eight outlets. Thus, according to the invention becomes a
Brennstoffdüsenanordnung geschaffen, welche in einen Aufsatz integriert wird und die somit alle Auslässe (Zerstäuberdüsen) umfasst. Somit wird also der Brennstoff in Einzelströme auf seinen Umfang unterteilt. Die Anzahl der auf der Scheibe an- geordneten Düseneinsätze und Aufnahmeeinheiten kann dabei variieren, auch die Anordnung der Düseneinsätze/Aufnahmeeinheiten auf der Scheibe.Fuel nozzle assembly created, which is integrated into an essay and thus includes all outlets (atomizer nozzles). Thus, therefore, the fuel is divided into individual streams on its circumference. The number of nozzle inserts and receiving units arranged on the disk can vary, as can the arrangement of the nozzle inserts / receiving units on the disk.
Bevorzugt besteht der Düseneinsatz und/oder die Aufnahmeein- heit aus Metall oder einer Metalllegierung. In bevorzugterThe nozzle insert and / or the receiving unit preferably consists of metal or a metal alloy. In preferred
Ausgestaltung bestehen der Düseneinsatz und/oder die Aufnahmeeinheit aus Keramik oder keramischen Material, da diese Materialien besonders abbriebbeständig sind.Embodiment consist of the nozzle insert and / or the receiving unit of ceramic or ceramic material, since these materials are particularly abrasion resistant.
Bevorzugt sind der Düseneinsatz und/oder die Aufnahmeeinheit feinmechanisch oder mit print-Technik herstellbar. Diese Herstellung ist besonders kostengünstig und schnell zu realisieren .Preferably, the nozzle insert and / or the receiving unit are fine mechanical or with print technology produced. This production is particularly inexpensive and quick to implement.
Weitere Vorteile, Merkmale und Eigenschaften der vorliegenden Erfindung werden im Folgenden anhand von Ausführungsbeispielen unter Bezugnahme auf die beigefügten Figuren näher be- schrieben. Die Merkmale der Ausführungsbeispiele können hierbei einzeln oder in Kombination miteinander vorteilhaft sein,Further advantages, features and characteristics of the present invention will be described in greater detail below on the basis of exemplary embodiments with reference to the attached figures. wrote. The features of the embodiments may be advantageous here individually or in combination with one another,
Fig. 1 zeigt schematisch eine Gasturbine in einem Längs- teilschnitt,1 schematically shows a gas turbine in a longitudinal partial section,
Fig. 2 zeigt schematisch einen Schnitt durch einen Brenner mit einer Düse nach dem Stand der Technik,2 shows schematically a section through a burner with a nozzle according to the prior art,
Fig. 3 zeigt schematisch einen erfindungsgemäßen Brennereinsatz,3 shows schematically a burner insert according to the invention,
Fig. 4,5 zeigt schematisch einen Aufsatz 13 mit 4 erfindungsgemäßen Brennereinsätzen in Rück- und Vorderansicht.Fig. 4.5 shows schematically an article 13 with 4 burner inserts according to the invention in back and front view.
Im Folgenden wird ein erstes Ausführungsbeispiel der vorliegenden Erfindung anhand der Figuren 1 bis 5 näher erläutert.In the following, a first exemplary embodiment of the present invention will be explained in more detail with reference to FIGS. 1 to 5.
Die Figur 1 zeigt beispielhaft eine Gasturbine 100 in einem Längsteilschnitt.FIG. 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
Die Gasturbine 100 weist im Inneren einen um eine Rotationsachse 102 drehgelagerten Rotor 103 mit einer Welle auf, der auch als Turbinenläufer bezeichnet wird.The gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft, which is also referred to as a turbine runner.
Entlang des Rotors 103 folgen aufeinander ein Ansauggehäuse 104, ein Verdichter 105, eine beispielsweise torusartige Brennkammer 110 mit mehreren koaxial angeordneten Brennern 107, eine Turbine 108 und das Abgasgehäuse 109.Along the rotor 103 successively follow an intake housing 104, a compressor 105, an example, toroidal combustion chamber 110 with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
Die Brennkammer 110 kommuniziert mit einem beispielsweise ringförmigen Heißgaskanal 111. Dort bilden beispielsweise vier hintereinander geschaltete Turbinenstufen 112 die Turbine 108.The combustion chamber 110 communicates with an annular annular hot gas channel 111, for example. There, for example, four turbine stages 112 connected in series form the turbine 108.
Jede Turbinenstufe 112 ist beispielsweise aus zwei Schaufelringen gebildet. In Strömungsrichtung eines Arbeitsmediums 113 gesehen folgt im Heißgaskanal 111 einer Leitschaufelreihe 115 eine aus Laufschaufeln 120 gebildete Reihe 125.Each turbine stage 112 is formed, for example, from two blade rings. In the flow direction of a working medium As can be seen in the hot gas duct 111 of a guide blade row 115, a row 125 formed of rotor blades 120 follows.
Die Leitschaufeln 130 sind dabei an einem Innengehäuse 138 eines Stators 143 befestigt, wohingegen die Laufschaufeln 120 einer Reihe 125 beispielsweise mittels einer Turbinenscheibe 133 am Rotor 103 angebracht sind.The guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
An dem Rotor 103 angekoppelt ist ein Generator oder eine Ar- beitsmaschine (nicht dargestellt) .Coupled to the rotor 103 is a generator or a work machine (not shown).
Während des Betriebes der Gasturbine 100 wird vom Verdichter 105 durch das Ansauggehäuse 104 Luft 135 angesaugt und verdichtet. Die am turbinenseitigen Ende des Verdichters 105 be- reitgestellte verdichtete Luft wird zu den Brennern 107 geführt und dort mit einem Brennstoff vermischt. Das Gemisch wird dann unter Bildung des Arbeitsmediums 113 in der Brennkammer 110 verbrannt. Von dort aus strömt das Arbeitsmedium 113 entlang des Heißgaskanals 111 vorbei an den Leitschaufeln 130 und den Laufschaufeln 120. An den Laufschaufeln 120 entspannt sich das Arbeitsmedium 113 impulsübertragend, so dass die Laufschaufeln 120 den Rotor 103 antreiben und dieser die an ihn angekoppelte Arbeitsmaschine.During operation of the gas turbine 100, air 105 is sucked in and compressed by the compressor 105 through the intake housing 104. The compressed air provided at the turbine-side end of the compressor 105 is guided to the burners 107 and mixed there with a fuel. The mixture is then burned to form the working fluid 113 in the combustion chamber 110. From there, the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120. On the rotor blades 120, the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
Die Figur 2 zeigt schematisch einen Schnitt durch einen Brenner 107 mit einer Düse nach dem Stand der Technik in teilweise perspektivischer Ansicht. Der Brenner 107 kann einerseits in Verbindung mit der Ringbrennkammer 106 verwendet werden. Vorzugsweise wird der Brenner 107 jedoch in Verbindung mit einer sogenannten Rohrbrennkammer verwendet. Hierbei weist die Gasturbine 100 anstelle der Ringbrennkammer 106 mehrere, ringförmig angeordnete Rohrbrennkammern auf, deren abström- seitigen Öffnungen in den ringförmigen Heißgaskanal 111 tur- bineneingansseitig münden. Dabei sind vorzugsweise an jeder dieser Rohrbrennkammer mehrere, beispielsweise sechs oder acht, Brenner 107 an dem gegenüberliegenden Ende der abstrom- seitigen Öffnung der Rohrbrennkammer zumeist ringförmig um einen Pilotbrenner angeordnet. Der Brenner 107 umfasst ein zylinderförmiges Gehäuse 12. In dem Gehäuse 12 ist entlang der Mittelachse 27 des Brenners 107 eine Lanze mit einem Brennstoffkanal 16 angeordnet. An der zur Brennkammer 110 hinführenden Seite der Lanze umfasst diese einen spitz ausgestalteten Aufsatz 13, der konzentrisch zur Mittelachse 27 angeordnet ist. In dem Aufsatz 13 sind die Brennstoffdüsen 1 nach dem Stand der Technik angeordnet, die mit dem Brennstoffkanal 16 kommunizieren.FIG. 2 schematically shows a section through a burner 107 with a nozzle according to the prior art in a partially perspective view. The burner 107 can be used on the one hand in conjunction with the annular combustion chamber 106. Preferably, however, the burner 107 is used in conjunction with a so-called tube combustion chamber. In this case, the gas turbine 100 has, instead of the annular combustion chamber 106, a plurality of annularly arranged tube combustion chambers whose outflow-side openings open into the annular hot gas channel 111 on the inlet side of the turbine. In this case, a plurality of, for example six or eight, burners 107 are preferably arranged on each of these tube combustion chambers at the opposite end of the downstream opening of the tube combustion chamber, usually annularly around a pilot burner. The burner 107 comprises a cylindrical housing 12. In the housing 12, a lance with a fuel channel 16 is arranged along the central axis 27 of the burner 107. On the side of the lance leading to the combustion chamber 110, the latter comprises a pointed attachment 13, which is arranged concentrically to the central axis 27. In the article 13, the fuel nozzles 1 are arranged according to the prior art, which communicate with the fuel channel 16.
In dem Gehäuse 12 des Brenners 107 sind um die Lanze herum Drallschaufeln 17 angeordnet. Die Drallschaufeln 17 sind entlang des Umfanges der Lanze in dem Gehäuse 12 angeordnet. Durch die Drallschaufeln 17 wird ein Verdichterluftstrom 15 in den zur Brennkammer 110 führenden Teil des Brenners 107 geleitet. Die Luft wird durch die Drallschaufeln 17 in eine Drallbewegung versetzt. In den dabei entstehenden Luftstrom wird Brennstoff, zum Beispiel Öl, durch die Brennstoffdüsen 1 eingedüst. Das dabei entstehende Brennstoff-Luft-Gemisch wird dann weiter in die Brennkammer 110 geleitet.In the housing 12 of the burner 107, swirl vanes 17 are arranged around the lance. The swirl blades 17 are arranged along the circumference of the lance in the housing 12. Through the swirl blades 17, a compressor air flow 15 is passed into the combustion chamber 110 leading to the part of the burner 107. The air is displaced by the swirl blades 17 in a swirling motion. Fuel, for example oil, is injected through the fuel nozzles 1 into the resulting air stream. The resulting fuel-air mixture is then passed on to the combustion chamber 110.
Die Figur 3 zeigt schematisch einen Schnitt durch eine erfindungsgemäße Brennstoffdüse . Die Düseneinsätze 1 sind am äußeren Umfang des Aufsatzes 13 in entsprechenden Aufnahmenein- heiten 4 angeordnet. Eine Brennstoffdüsenanordnung umfasst mehrere, im vorliegenden Ausführungsbeispiel vier, erfindungsgemäße Düseneinsätze 1 mit entsprechenden Aufnahmeeinheiten 4 (Figur 4, Rückansicht und Figur 5 Vorderansicht) . Die Strömungspfade 5 sind dabei als vier Schlitze angedeutet (Figur 4, Figur 5) .FIG. 3 schematically shows a section through a fuel nozzle according to the invention. The nozzle inserts 1 are arranged on the outer circumference of the attachment 13 in corresponding receiving units 4. A fuel nozzle arrangement comprises a plurality of, in the present embodiment, four nozzle inserts 1 according to the invention with corresponding receiving units 4 (FIG. 4, rear view and FIG. 5 front view). The flow paths 5 are indicated here as four slots (FIG. 4, FIG. 5).
Die Mittelachse des Aufsatzes 13 ist durch die Bezugsziffer 18 gekennzeichnet. Der Aufsatz 13 ist zur Brennkammer 110 hin kegelförmig, spitz zulaufend ausgestaltet. Der Düseneinsatz 1 ist am äußeren Umfang des Aufsatzes 13 in den entsprechenden Aufnahmeneinheiten 4 angeordnet und bildet damit die Drallkammern 10. Der erfindungsgemäße Düseneinsatz 1 ist als integriertes Bauteil angefertigt. Der erfindungsgemäße Düsen- einsatz 1 umfasst an seinem Brennstoffeinlass 2, welcher sich in der Drallkammer 10 befindet etwa einen halbkreisförmig gebogenen Eintrittsanfang 7a sowie ein Ende 7b. Der Düseneinsatz 1 weist einen Düseneinsatzhals 3 auf. Der Düseneinsatz 1 insbesondere der Düseneinsatzhals 3 selber sowie der bevorzugt kreisförmig gebogene Eintrittsanfang 7a bilden mit der Aufnahmeneinheit 4 einen Strömungspfad 5 aus, entlang dessen der Brennstoff strömen kann. Der Eintrittsanfang 7a und das Ende 7b bilden mit der Aufnahmeneinheit 4 die Drallkammer 10 aus. Dabei kann der Strömungspfad 5 welcher durch den Eintrittsanfang 7a des Düseneinsatzes 1 und die AufnahmeeinheitThe central axis of the attachment 13 is indicated by the reference numeral 18. The attachment 13 is conical to the combustion chamber 110, tapered designed. The nozzle insert 1 is arranged on the outer circumference of the attachment 13 in the corresponding receiving units 4 and thus forms the swirl chambers 10. The nozzle insert 1 according to the invention is made as an integrated component. The nozzle according to the invention Insert 1 comprises at its fuel inlet 2, which is located in the swirl chamber 10 approximately a semicircular curved inlet beginning 7a and an end 7b. The nozzle insert 1 has a nozzle insert neck 3. The nozzle insert 1, in particular the nozzle insert neck 3 itself and the preferably circularly curved inlet beginning 7a, form with the receiving unit 4 a flow path 5, along which the fuel can flow. The entry start 7a and the end 7b form with the receiving unit 4, the swirl chamber 10 from. In this case, the flow path 5 which through the inlet beginning 7a of the nozzle insert 1 and the receiving unit
4 gebildet wird, sich in Strömungsrichtung verjüngen oder auch erweitern. Bei einer Erweiterung des Strömungspfades 5 ist das halbkreisförmig gebogene Eintrittsanfang 7a im We- sentlichen zu einem Auslass 8 hin gebogen. Der Brennstoff, der durch den Strömungspfad 5 strömt, wird daraufhin zur Mitte abgelenkt. Bei einer Verjüngung bildet der Eintrittsanfang 7a von dem Auslass weggebogen und verjüngt den Strömungspfad4 is formed, taper in the flow direction or expand. When the flow path 5 is widened, the semicircularly curved entry start 7a is bent essentially toward an outlet 8. The fuel flowing through the flow path 5 is then deflected toward the center. At a taper, the inlet beginning 7a is bent away from the outlet and tapers the flow path
5 damit. Die Strömungsgeschwindigkeit wird erhöht. Die Erhö- hung kann auch dadurch stattfinden, dass sich die Tiefe der5 with it. The flow rate is increased. The increase can also take place in that the depth of the
Aufnahmeneinheit 4 am Eintrittsanfang 7a in Strömungsrichtung verändert, bevorzugt verringert. Dabei ist eine lineare Verringerung oder auch eine nichtlineare Verringerung möglich. Die Drallkammer 10 ist im Wesentlichen kreisförmig ausgebil- det. Der Strömungspfad 5 führt am Eintrittsanfang 7a in der Drallkammer 10 durch diese Anordnung also eine kreisförmige Bewegung aus, welche den Brennstoff in Richtung Auslass 8 lenkt. Der Brennstoff führt also eine kreisförmige Bewegung aus, das heißt der Brennstoff wird somit kreis-, insbesondere spiralförmig 12 verwirbelt. Anschließend tritt der so verwirbelte Brennstoff zum Zwecke der Zerstäubung durch den Auslass 8 hinaus. Dabei ist der Auslass 8 eine Querbohrung zum Zwecke der Ausströmung.Pick unit 4 at the inlet beginning 7a changed in the flow direction, preferably reduced. In this case, a linear reduction or a non-linear reduction is possible. The swirl chamber 10 is essentially circular. The flow path 5 thus performs at the inlet beginning 7a in the swirl chamber 10 by this arrangement a circular movement, which directs the fuel towards the outlet 8. The fuel thus performs a circular movement, that is, the fuel is thus circular, in particular spiral 12 swirled. Subsequently, the so-swirled fuel passes through the outlet 8 for the purpose of atomization. In this case, the outlet 8 is a transverse bore for the purpose of outflow.
Der erfindungsgemäße Düseneinsatz 1 erzeugt so eine BrennstoffStrömung insbesondere eine Flüssigkeitsbrennstoffströmung mit einer Drallkomponente in den Kammern stromabwärts . Mit der erfindungsgemäßen Lösung wird somit eine Brennstoffdüse durch einen in einer Aufnahmeeinheit 4 integrierbaren Düseneinsatz 1 geschaffen. Insbesondere wird eine Scheibe mit einer erfindungsgemäßen Brennstoffdüsenanordnung geschaffen, welche in einen Aufsatz 13 oder ein anderes Bauteil eingesetzt wird und somit alle Auslässe 8 (Zerstäubungsöffnungen) des Aufsatzes 13 versorgt. Die Brennstoffdüse bzw. die Brennstoffdüsenanordnung teilt den Brennstoffström in Einzelströme verteilt auf den Umfang. Die bisher eingesetzten Düsen dienen zur Drallerzeugung in der Strömung des Brennstoffes bevor dieser in die Brennkammer gelangt. Der Drall wird nun mittels der speziellen Geometrie der erfindungsgemäßen Brennstoffdüse erzeugt. Die Brennstoffdüse bzw. die Aufnahmeeinheit und/oder der Düseneinsatz kann aus metallischen oder auch keramischen Materialien feinmechanisch oder „print"-basiert hergestellt werden .The nozzle insert 1 according to the invention thus generates a flow of fuel, in particular a liquid fuel flow with a swirl component in the chambers downstream. With the solution according to the invention, a fuel nozzle is thus created by a nozzle insert 1 which can be integrated in a receiving unit 4. In particular, a disk with a fuel nozzle arrangement according to the invention is provided, which is inserted into an attachment 13 or another component and thus supplies all the outlets 8 (atomization openings) of the attachment 13. The fuel nozzle or the fuel nozzle arrangement divides the Brennstoffström distributed in individual streams on the circumference. The previously used nozzles are used for swirl generation in the flow of the fuel before it enters the combustion chamber. The twist is now generated by means of the special geometry of the fuel nozzle according to the invention. The fuel nozzle or the receiving unit and / or the nozzle insert can be made of metallic or ceramic materials fine mechanical or "print" -based.
Wahlweise kann im Strömungspfad 5 eine Beschleunigung des Brennstoffes stattfinden, um so größte Geschwindigkeit erst am Eintritt in die Drallkammer 10 zu erhalten, so dass zu hohe Druckverluste und Kavitation vermieden werden und man so einen effektiven Düsenquerschnitt erhält, der unabhängiger vom Durchsatz ist. Dies kann beispielsweise erreicht werden, in dem der Eintrittsanfang 7a zur Auslassmitte 8 gebogen wird oder von der Auslassmitte 8 weggebogen wird oder/und indem sich die Tiefe der Aufnahmeneinheit 4 bei Eintrittsanfang 7a ändert . Optionally, in the flow path 5, an acceleration of the fuel take place, so as to obtain maximum speed only at the entrance to the swirl chamber 10, so that too high pressure losses and cavitation are avoided and one thus obtains an effective nozzle cross section, which is more independent of the throughput. This can be achieved, for example, by bending the inlet beginning 7a to the outlet center 8 or bending it away from the outlet center 8 and / or by changing the depth of the receiving unit 4 at the entrance beginning 7a.

Claims

Patentansprüche claims
1. Brennstoffdüse zur Verdrallung eines Brennstoffs/Brennstoff-Luft Gemisches, umfassend einer Aufnahmeeinheit (4) und einem Düseneinsatz (1), wobei der Düseneinsatz (1) und die Aufnahmeeinheit (4) einen Strömungspfad (5) und anschließend eine Drallkammer (10) ausbilden, wobei der Düseneinsatz (1) ein Eintrittsanfang (7a) und ein Ende (7b) aufweist, wobei der Eintrittsan- fang (7a) und das Ende (7b) im Wesentlichen kreisförmig gebogen ist, so dass ein unterbrochener Kreis gebildet ist, so dass einem in die Drallkammer (10) hineinströmender Brennstoff eine radial einwärts gerichtete Kreis-, insbesondere Spiralbewegung (12) aufgeprägt wird.1. A fuel nozzle for twisting a fuel / fuel-air mixture, comprising a receiving unit (4) and a nozzle insert (1), wherein the nozzle insert (1) and the receiving unit (4) has a flow path (5) and then a swirl chamber (10). form, wherein the nozzle insert (1) has a Eintrittsanfang (7a) and an end (7b), wherein the inlet (7a) and the end (7b) is bent substantially circular, so that an interrupted circle is formed, so that a radially inwardly directed circular, in particular spiral movement (12) is impressed on a fuel flowing into the swirl chamber (10).
2. Brennstoffdüse nach Anspruch 1, dadurch gekennzeichnet, dass sich die Tiefe der Aufnahmeneinheit (4) am Eintrittsanfang (7a) des Düseneinsatzes (1) in Strömungsrichtung verringert, so dass eine Änderung der Strö- mungsgeschwindigkeit des Brennstoffs bewirkt ist.2. Fuel nozzle according to claim 1, characterized in that the depth of the receiving unit (4) at the inlet beginning (7 a) of the nozzle insert (1) decreases in the flow direction, so that a change in the flow speed of the fuel is effected.
3. Brennstoffdüse nach einem der Ansprüche 1-2, dadurch gekennzeichnet, dass sich der Strömungspfad (5) welcher durch den Eintrittsanfang (7a) des Düseneinsatzes (1) und die Aufnahmeeinheit (4) gebildet wird, in Strömungsrichtung verjüngt.3. The fuel nozzle according to any one of claims 1-2, characterized in that the flow path (5) which is formed by the inlet beginning (7 a) of the nozzle insert (1) and the receiving unit (4), tapers in the flow direction.
4. Brennstoffdüse nach einem der Ansprüche 1-2, dadurch gekennzeichnet, dass sich der Strömungspfad (5) wel- eher durch den Eintrittsanfang (7a) des Düseneinsatzes (1) und die Aufnahmeeinheit (4) gebildet wird, in Strömungsrichtung erweitert.4. The fuel nozzle according to any one of claims 1-2, characterized in that the flow path (5) wel- rather by the inlet beginning (7a) of the nozzle insert (1) and the receiving unit (4) is formed, expanded in the flow direction.
5. Brennstoffdüse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Düseneinsatz (1) als integriertes Bauteil in die Aufnahmeneinheit (4) einsetzbar ist. 5. Fuel nozzle according to one of the preceding claims, characterized in that the nozzle insert (1) can be inserted as an integrated component in the receiving unit (4).
6. Brennstoffdüse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Aufnahmeeinheit (4) und/oder der Düseneinsatz (1) aus Metall oder einer Metalllegierung besteht .6. Fuel nozzle according to one of the preceding claims, characterized in that the receiving unit (4) and / or the nozzle insert (1) consists of metal or a metal alloy.
7. Brennstoffdüse nach einem der Ansprüche 1-6, dadurch gekennzeichnet, dass die Aufnahmeeinheit (4) und/oder der Düseneinsatz (1) aus Keramik oder keramischen Material besteht .7. The fuel nozzle according to any one of claims 1-6, characterized in that the receiving unit (4) and / or the nozzle insert (1) consists of ceramic or ceramic material.
8. Brennstoffdüse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Aufnahmeeinheit (4) und/oder der Düseneinsatz (1) feinmechanisch oder mit print-Technik herstellbar ist.8. The fuel nozzle according to one of the preceding claims, characterized in that the receiving unit (4) and / or the nozzle insert (1) can be produced with precision engineering or with print technology.
9. Brennstoffdüse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Drallkammer (10) kreisförmig ausgebildet ist.9. Fuel nozzle according to one of the preceding claims, characterized in that the swirl chamber (10) is circular.
10. Brennstoffdüse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Drallkammer (10) einen Aus- lass (8) umfasst, so dass der Brennstoff/Brennstoff-Luft Gemisch verdrallt dort austreten kann.10. The fuel nozzle according to any one of the preceding claims, characterized in that the swirl chamber (10) comprises an outlet (8), so that the fuel / air-fuel mixture twisted can escape there.
11. Brennstoffdüse nach Anspruch 10, dadurch gekennzeichnet, dass der Auslass (8) eine Bohrung ist .11. A fuel nozzle according to claim 10, characterized in that the outlet (8) is a bore.
12. Brennstoffdüsenanordnung, dadurch gekennzeichnet, dass diese vier -acht im Wesentlichen symmetrisch auf einer Scheibe angeordnete Brennstoffdüsen nach einem der vorhergehenden Ansprüche umfasst.12. A fuel nozzle assembly, characterized in that said four-eight substantially symmetrically arranged on a disc fuel nozzles according to one of the preceding claims.
13. Brenner (107), der zumindest einer Brennstoffdüsenanord- nung nach Anspruch 12 umfasst.13. Burner (107) comprising at least one fuel nozzle arrangement according to claim 12.
14. Brenner (107) nach Anspruch 13, der ein zylinderförmiges Gehäuse (12) mit einer darin zentral angeordneten, einen Brennstoffkanal (16) aufweisende Lanze umfasst, welche über strahlenartig angeordnete Drallschaufeln (17) am Gehäuse abgestützt ist und an der zu einer Brennkammer hinführenden Seite ein Aufsatz (13) angeordnet ist, wobei die Brennstoffdüsenanordnung in dem Aufsatz (13) vorzugsweise stromab der Drallschaufeln (17) angeordnet und strömungstechnisch mit dem Brennstoffkanal (16) verbunden sind.14. Burner (107) according to claim 13, which has a cylindrical housing (12) with a centrally located therein arranged, a fuel channel (16) having a lance, which is supported via radially arranged swirl vanes (17) on the housing and on the side leading to a combustion chamber an attachment (13) is arranged, wherein the fuel nozzle assembly in the attachment (13) preferably downstream the swirl vanes (17) are arranged and fluidically connected to the fuel channel (16).
15. Brenneranordnung mit mehreren, auf ringförmig um einen zentralen Pilotbrenner angeordneten Brennern (107) nach einem der Ansprüche 13 bis 14.15. Burner arrangement with a plurality of annularly arranged around a central pilot burner burners (107) according to one of claims 13 to 14.
16. Gasturbine (100), die zumindest einen Brenner (107) nach einem der Ansprüche 13 bis 14 oder die für jede Rohr- brennkammer eine Brenneranordnung nach Anspruch 15 umfasst. 16. A gas turbine (100) comprising at least one burner (107) according to any one of claims 13 to 14 or for each tube combustion chamber, a burner assembly according to claim 15.
EP09779477.0A 2008-08-11 2009-05-14 Fuel nozzle insert Not-in-force EP2310741B1 (en)

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EP08014308A EP2154428A1 (en) 2008-08-11 2008-08-11 Fuel nozzle insert
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PCT/EP2009/055827 WO2010018013A2 (en) 2008-08-11 2009-05-14 Fuel insert

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WO2010018013A2 (en) 2010-02-18
EP2310741B1 (en) 2015-02-25
EP2154428A1 (en) 2010-02-17
US20110136067A1 (en) 2011-06-09
WO2010018013A3 (en) 2010-08-05

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